CA2717827A1 - Abradable coating system - Google Patents
Abradable coating system Download PDFInfo
- Publication number
- CA2717827A1 CA2717827A1 CA2717827A CA2717827A CA2717827A1 CA 2717827 A1 CA2717827 A1 CA 2717827A1 CA 2717827 A CA2717827 A CA 2717827A CA 2717827 A CA2717827 A CA 2717827A CA 2717827 A1 CA2717827 A1 CA 2717827A1
- Authority
- CA
- Canada
- Prior art keywords
- abradable coating
- abradable
- woven
- ceramic
- coating system
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
- F01D11/125—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material with a reinforcing structure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/005—Repairing methods or devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/284—Selection of ceramic materials
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/90—Coating; Surface treatment
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/21—Oxide ceramics
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/601—Fabrics
- F05D2300/6012—Woven fabrics
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/612—Foam
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/615—Filler
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Ceramic Engineering (AREA)
- Materials Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Laminated Bodies (AREA)
Abstract
An abradable coating system (2-8) for a turbine or a compressor is proposed comprising at least one layer of woven or non-woven tissue (15) or foam made of a material selected from the group of. ceramic, glass, glass-ceramic, ceramic-metal composite and combinations thereof. Further a free-standing preformed element (18) comprising at least one layer of such a woven or non-woven tissue or foam is proposed filled with fillers and/or binder. Further a method for the preparation of such a system is disclosed. Finally a method for the repair of an abradable coating portion of a turbine or the compressor component (9) is disclosed, wherein in a first optional step the damaged portion is at least partly removed and/or cleaned and/or surface treated, and wherein in a second step at least one free-standing preformed abradable coating element (18) or a complete abradable coating system is attached to the component (9), preferably by using a matrix, wherein for example only a centre part (2) or a fraction of a centre part (2) is replaced.
Description
TITLE
Abradable coating system TECHNICAL FIELD
The present invention relates to an abradable coating system, free-standing preformed element therefore, as well as to methods for making such system/preformed elements and to turbine and compressor components comprising such structures and to a repair scheme.
PRIOR ART
Compressors and turbines of gas and steam turbine engines are provided with abradable coatings at several positions. Abradable coatings are, for example, provided on the radial inner surfaces of compressor and/or turbine stator components.
Abradable coatings in this context are e.g. known from EP 1 392 957; EP 1 734 146; EP 1 975 271; EP 1 273 675; WO03/010419; US2005/0123785; US2009/0148278; US6457939.
SUMMARY OF THE INVENTION
It is therefore one object of the present invention, to provide an improved abradable coating system to be mounted on a turbine or compressor component as well as elements therefore and methods for making such an abradable coating system, and in addition to that a method for repairing an abradable coating system, preferably in an on-site repair process.
This in relation to blade sealing against the stator heat shield, but also to vane sealing against the rotor.
This object is achieved by the proposed abradable coating system, a free-standing preformed abradable coating system element and the methods according to the appended claims.
In the state-of-the-art, there are limitations in the design due to the materials and the processes used. The present invention proposes a design and related process/materials, which enables, among others, a more efficient clearance and a flexible coating solution,
Abradable coating system TECHNICAL FIELD
The present invention relates to an abradable coating system, free-standing preformed element therefore, as well as to methods for making such system/preformed elements and to turbine and compressor components comprising such structures and to a repair scheme.
PRIOR ART
Compressors and turbines of gas and steam turbine engines are provided with abradable coatings at several positions. Abradable coatings are, for example, provided on the radial inner surfaces of compressor and/or turbine stator components.
Abradable coatings in this context are e.g. known from EP 1 392 957; EP 1 734 146; EP 1 975 271; EP 1 273 675; WO03/010419; US2005/0123785; US2009/0148278; US6457939.
SUMMARY OF THE INVENTION
It is therefore one object of the present invention, to provide an improved abradable coating system to be mounted on a turbine or compressor component as well as elements therefore and methods for making such an abradable coating system, and in addition to that a method for repairing an abradable coating system, preferably in an on-site repair process.
This in relation to blade sealing against the stator heat shield, but also to vane sealing against the rotor.
This object is achieved by the proposed abradable coating system, a free-standing preformed abradable coating system element and the methods according to the appended claims.
In the state-of-the-art, there are limitations in the design due to the materials and the processes used. The present invention proposes a design and related process/materials, which enables, among others, a more efficient clearance and a flexible coating solution,
2 which can be adjusted for all engines and all operation conditions due to the absence of limitation for the coating thickness. Further there are less risks of damage of blade tip/vane tip, coating spallation and erosion due to the structuring. Some important technical differentiations are the controlled properties on the micrometer, millimeter and centimeter range in the 3 dimensions, which implies a better abradability and mechanical integrity.
This is achieved with a customized combination of the tissue and the impregnated matrix providing an unexpected optimum compromise between abradability and erosion.
Indeed, for example none of the constructions mentioned above enables to successfully achieve mechanical integrity of the system and efficient clearance reduction of 2 mm and more. The present invention therefore proposes a 3D-graded design and provides an abradable coating with superior abradability and spallation resistance.
Customized abradable properties are for example achieved by:
= a gradient along z (radial direction of the turbine/compressor) achieved on a millimeter scale by the impregnation of the tissue or the different tissues and impregnation matrix;
= a foam or a fibre structure in the form of a woven or non-woven tissue used is distributed such that it is oriented essentially along y (circumferential direction);
= a controlled porosity, which results from the combination of the used tissue and the impregnation matrix in the plane x-y;
Spalling/erosion resistance is for example achieved by:
= the gradient along z achieved on a millimeter scale by the impregnation into the tissue or the different tissues and impregnation matrix.
= the structure along x-y on a centimeter scale.
Further the present invention provides an abradable coating with a controlled thickness within a small tolerance in order to obtain an optimal clearance reduction and simultaneously to reduce the risk of blade/vane damage.
The proposed invention also takes into account the needs for a fine structure.
It provides a texture on the micrometer range. The structure (pores and optionally fiber direction) in the micrometer range is beneficial in terms of reduced localized damages, abradability and erosion resistance. The structure in the micrometer range is for example achieved by:
= the orientation of the fibers of the tissue;
= the inherent porosity to the tissue or foam;
This is achieved with a customized combination of the tissue and the impregnated matrix providing an unexpected optimum compromise between abradability and erosion.
Indeed, for example none of the constructions mentioned above enables to successfully achieve mechanical integrity of the system and efficient clearance reduction of 2 mm and more. The present invention therefore proposes a 3D-graded design and provides an abradable coating with superior abradability and spallation resistance.
Customized abradable properties are for example achieved by:
= a gradient along z (radial direction of the turbine/compressor) achieved on a millimeter scale by the impregnation of the tissue or the different tissues and impregnation matrix;
= a foam or a fibre structure in the form of a woven or non-woven tissue used is distributed such that it is oriented essentially along y (circumferential direction);
= a controlled porosity, which results from the combination of the used tissue and the impregnation matrix in the plane x-y;
Spalling/erosion resistance is for example achieved by:
= the gradient along z achieved on a millimeter scale by the impregnation into the tissue or the different tissues and impregnation matrix.
= the structure along x-y on a centimeter scale.
Further the present invention provides an abradable coating with a controlled thickness within a small tolerance in order to obtain an optimal clearance reduction and simultaneously to reduce the risk of blade/vane damage.
The proposed invention also takes into account the needs for a fine structure.
It provides a texture on the micrometer range. The structure (pores and optionally fiber direction) in the micrometer range is beneficial in terms of reduced localized damages, abradability and erosion resistance. The structure in the micrometer range is for example achieved by:
= the orientation of the fibers of the tissue;
= the inherent porosity to the tissue or foam;
3 = the impregnation matrix.
The structure in the millimeter range is beneficial for strain tolerance, mechanical integrity, a more efficient clearance reduction. It is achieved by:
= designing the impregnation into the tissue = combining differently impregnated tissues together = texturing the surface The structure in the centimeter range is beneficial for mechanical integrity.
It is achieved by:
= designing the impregnation material into the tissue on the side of the component.
More specifically, the present invention relates to an abradable coating system for a turbine or a compressor (steam turbines or gas turbines being possible, also inclusive of turbomachines with compressor and turbine) comprising at least one layer of woven or non-woven tissue based on fibers or foam made of a material selected from the group of:
ceramic, glass, glass-ceramic, ceramic-metal composite and combinations thereof in combination with an impregnation material (forming a matrix) comprising filler particles or filler fibres, e.g. made of materials selected from the group of: ceramic, glass, glass-ceramic, ceramic-metal composite and a binder selected from the group of organic and/or inorganic polymers. The abradable coating system can be applied to a turbine or compressor component. The expression filler particle also includes filler fibres.
For example, it is possible to use a felt made of YSZ fibers and impregnated with a slurry made of alumina precursors, YSZ and silicate.
So the impregnation material or matrix comprises filler particles and/or filler fibres as well as at least one binder. The matrix can be applied as a slurry. Organic binders will normally essentially disappear/decompose due to heat treatment and/or operation of the turbine/compressor.
Preferentially, at least in the surface region of the system it comprises a stripe-like circumferential centre part bordered, preferably at both sides, in axial direction, by a stripe-like circumferential side parts.
The centre part or core is highly abradable such that it is essentially abraded without blading tip reinforcement as soon as the blading tip is running into the coating. The running in can occur during a run-in procedure or after few hours of operation or after several thousands of hours when rotor sagging or ovalisation occur.
The structure in the millimeter range is beneficial for strain tolerance, mechanical integrity, a more efficient clearance reduction. It is achieved by:
= designing the impregnation into the tissue = combining differently impregnated tissues together = texturing the surface The structure in the centimeter range is beneficial for mechanical integrity.
It is achieved by:
= designing the impregnation material into the tissue on the side of the component.
More specifically, the present invention relates to an abradable coating system for a turbine or a compressor (steam turbines or gas turbines being possible, also inclusive of turbomachines with compressor and turbine) comprising at least one layer of woven or non-woven tissue based on fibers or foam made of a material selected from the group of:
ceramic, glass, glass-ceramic, ceramic-metal composite and combinations thereof in combination with an impregnation material (forming a matrix) comprising filler particles or filler fibres, e.g. made of materials selected from the group of: ceramic, glass, glass-ceramic, ceramic-metal composite and a binder selected from the group of organic and/or inorganic polymers. The abradable coating system can be applied to a turbine or compressor component. The expression filler particle also includes filler fibres.
For example, it is possible to use a felt made of YSZ fibers and impregnated with a slurry made of alumina precursors, YSZ and silicate.
So the impregnation material or matrix comprises filler particles and/or filler fibres as well as at least one binder. The matrix can be applied as a slurry. Organic binders will normally essentially disappear/decompose due to heat treatment and/or operation of the turbine/compressor.
Preferentially, at least in the surface region of the system it comprises a stripe-like circumferential centre part bordered, preferably at both sides, in axial direction, by a stripe-like circumferential side parts.
The centre part or core is highly abradable such that it is essentially abraded without blading tip reinforcement as soon as the blading tip is running into the coating. The running in can occur during a run-in procedure or after few hours of operation or after several thousands of hours when rotor sagging or ovalisation occur.
4 When talking about blading direction and blading tip reinforcement generally this shall include blading in the broad sense. So it shall include rotating blades and the corresponding associated sealing on stationary parts of the machine, as well as stationary vanes and the corresponding associated sealing on rotating parts of the machine (e.g. on the rotor). When talking about rotation direction of the blades or rotation of blade, this shall include the corresponding situation with vanes, so also the rotation direction of the rotor with respect to the vanes.
On the other hand the side part(s) are less or essentially not abradable and erosion resistant.
Preferentially the centre part has a width in the axial direction essentially at least identical to one third of the width of the tip portion of the corresponding blade/vane, which may contact and rub. Clearly the whole width of the system including the side parts is normally at least as wide as the width of the corresponding blade/vane tip width.
In the centre part the abradability can be graded along a radial direction z (radial with respect to the turbine/compressor axis), preferably on the millimeter scale, such that in the surfacial region of the system it is more abradable than on the side facing the turbine or compressor component on which the system is mounted The surface of the centre part can be provided with a surface texturing with dimensions along the radial direction z with respect to the turbine axis in the range of 0.2-4 mm, preferably in the range of 1-2 mm. This surface texturing can be generated by isostatic hot pressing or by using polymers or by applying a material similar to the impregnation matrix.
The differentiation between centre part and side part(s) can for example also be provided by using for both parts the same materials but providing a surface texturing in the centre part only.
The differentiation between the centre part of the side parts can also be achieved by using the same tissue but by using a different impregnation matrix material and/or a different degree of impregnation (see further below).
The fibers of the woven or non-woven tissue are preferentially essentially aligned along the rotation direction, so in a circumferential direction. Preferably in this case at least in the surface region the system comprises a stripe-like circumferentially oriented centre part based on a layer of woven or non-woven impregnated tissue bordered, typically at both sides in axial direction, by a stripe-like circumferentially oriented side part, wherein at least in the centre part the fibers of the woven or non-woven tissue are essentially aligned along the rotation direction and wherein the centre part is highly abradable such that it is preferably abraded without blading tip reinforcement, and wherein the side part(s) are less abradable and are preferably essentially erosion resistant. Again preferably the centre part has a width in the axial direction at least identical to one third of the width of the tip
On the other hand the side part(s) are less or essentially not abradable and erosion resistant.
Preferentially the centre part has a width in the axial direction essentially at least identical to one third of the width of the tip portion of the corresponding blade/vane, which may contact and rub. Clearly the whole width of the system including the side parts is normally at least as wide as the width of the corresponding blade/vane tip width.
In the centre part the abradability can be graded along a radial direction z (radial with respect to the turbine/compressor axis), preferably on the millimeter scale, such that in the surfacial region of the system it is more abradable than on the side facing the turbine or compressor component on which the system is mounted The surface of the centre part can be provided with a surface texturing with dimensions along the radial direction z with respect to the turbine axis in the range of 0.2-4 mm, preferably in the range of 1-2 mm. This surface texturing can be generated by isostatic hot pressing or by using polymers or by applying a material similar to the impregnation matrix.
The differentiation between centre part and side part(s) can for example also be provided by using for both parts the same materials but providing a surface texturing in the centre part only.
The differentiation between the centre part of the side parts can also be achieved by using the same tissue but by using a different impregnation matrix material and/or a different degree of impregnation (see further below).
The fibers of the woven or non-woven tissue are preferentially essentially aligned along the rotation direction, so in a circumferential direction. Preferably in this case at least in the surface region the system comprises a stripe-like circumferentially oriented centre part based on a layer of woven or non-woven impregnated tissue bordered, typically at both sides in axial direction, by a stripe-like circumferentially oriented side part, wherein at least in the centre part the fibers of the woven or non-woven tissue are essentially aligned along the rotation direction and wherein the centre part is highly abradable such that it is preferably abraded without blading tip reinforcement, and wherein the side part(s) are less abradable and are preferably essentially erosion resistant. Again preferably the centre part has a width in the axial direction at least identical to one third of the width of the tip
5 portion of the corresponding blading potentially coming into contact with the seal when rotating.
The layer of woven or non-woven tissue or foam is, according to yet another preferred embodiment, at least partly impregnated by a matrix material of a composition of optionally filler particles/fibres and binder, wherein preferably the filler particles/fibres are metal, ceramic, glass, glass-ceramic, oxide precursors and/or wherein preferably optionally the binder is an organic and/or inorganic polymer.
Examples (without being not limited to these) of filler particles/fibres are YSZ, A1203, SiO2, aluminum hydroxide, SiC, Ce02, Aluminum toughened zirconia.
Examples (without being not limited to these) of inorganic binders are alkali silicate, alumino silicate, aluminum phosphate and for organic binders polyvinyl butyrol. The organic binders typically decompose upon heat treatment/sintering or during operation of the turbine/compressor.
A system as described above can, according to yet another preferred embodiment, be applied as a monoblock or as an assembly of several blocks on a turbine or compressor component. Preferably it is applied on a stator heat shield on a metal or ceramic surface.
According to a preferred embodiment, the system is applied on the component with a matrix (e.g. applied as a slurry) then acting as a glue, preferably a curable matrix cured by irradiation and/or heat.
The system can also be a stratified multilayer element of several laminated layers, which has a total height in a radial direction (z) in the range of 0.2-4 mm, preferably in the range of 1-2 mm, wherein preferentially individual abradable coating material layers have typically a thickness in the range of 0.1-0.4 mm. The proposed system can also be provided with cooling elements, wherein preferably these cooling elements are provided as channels and/or grooves in the monoblock or assembly of several block structures. Such cooling channels can for example be provided on the side facing away from the hot gas channel such that between the component and the abradable coating system cooling medium, normally cooling air, can flow.
The layer of woven or non-woven tissue or foam is, according to yet another preferred embodiment, at least partly impregnated by a matrix material of a composition of optionally filler particles/fibres and binder, wherein preferably the filler particles/fibres are metal, ceramic, glass, glass-ceramic, oxide precursors and/or wherein preferably optionally the binder is an organic and/or inorganic polymer.
Examples (without being not limited to these) of filler particles/fibres are YSZ, A1203, SiO2, aluminum hydroxide, SiC, Ce02, Aluminum toughened zirconia.
Examples (without being not limited to these) of inorganic binders are alkali silicate, alumino silicate, aluminum phosphate and for organic binders polyvinyl butyrol. The organic binders typically decompose upon heat treatment/sintering or during operation of the turbine/compressor.
A system as described above can, according to yet another preferred embodiment, be applied as a monoblock or as an assembly of several blocks on a turbine or compressor component. Preferably it is applied on a stator heat shield on a metal or ceramic surface.
According to a preferred embodiment, the system is applied on the component with a matrix (e.g. applied as a slurry) then acting as a glue, preferably a curable matrix cured by irradiation and/or heat.
The system can also be a stratified multilayer element of several laminated layers, which has a total height in a radial direction (z) in the range of 0.2-4 mm, preferably in the range of 1-2 mm, wherein preferentially individual abradable coating material layers have typically a thickness in the range of 0.1-0.4 mm. The proposed system can also be provided with cooling elements, wherein preferably these cooling elements are provided as channels and/or grooves in the monoblock or assembly of several block structures. Such cooling channels can for example be provided on the side facing away from the hot gas channel such that between the component and the abradable coating system cooling medium, normally cooling air, can flow.
6 In addition to that the present invention relates to a component a turbine or a compressor with such an abradable coating system mounted thereon.
In addition to that the present invention relates to a free-standing preformed for a turbine or a compressor comprising at least one layer of woven or non-woven tissue or foam made of a material selected from the group of: ceramic, glass, ceramic-metal composite material, and combinations thereof, wherein preferably the fibers of the woven or preferably non-woven tissue are essentially aligned along one specific direction.
The present invention also relates to a (on-site or off-site) method for the manufacturing of a system or a free-standing preformed as described above, wherein in a first step at least one free-standing preformed abradable coating element for a turbine or a compressor comprising at least one layer of woven or non-woven tissue or foam material based on fibers made of a material selected from the group of. ceramic, glass, ceramic-metal composite material, and combinations thereof, is made, optionally combined and joined with one or several additional such free-standing preformed abradable coating elements, and wherein in a second optional step the abradable coating system is attached to a turbine or compressor component with a matrix acting as a glue or adhesion promoter, preferably a curable glue cured by irradiation and/or heat.
In the first step of making the free-standing preformed abradable coating element and/or after the second step of attachment thereof on the gas turbine or compressor component the woven or nonwoven tissue or foam can, according to a preferred embodiment of the method, at least partly be embedded in or impregnated with a matrix of a composition of filler particles/fibres and binder, wherein preferably the filler particles/fibres are oxides or oxide precursors and/or wherein preferably the binder is an organic and/or inorganic polymer, and wherein preferably the matrix material is immersed into the tissue material in liquid state and hardened therein. A grading along the radial direction of the turbine and/or compressor in the final coating element can be achieved by differential immersion and/or differential choice of matrix material and/or by using differentially structured layers in the stack of several layers.
A multitude of free-standing, preformed abradable coating element layers with a thickness of up to 4 mm can be produced and subsequently laminated by using for example an adhesion layer to form a final abradable coating system, preferably with a total height in a radial direction (z) in the range of 0.2-4 mm, preferably in the range of 1-2 mm.
In addition to that the present invention relates to a free-standing preformed for a turbine or a compressor comprising at least one layer of woven or non-woven tissue or foam made of a material selected from the group of: ceramic, glass, ceramic-metal composite material, and combinations thereof, wherein preferably the fibers of the woven or preferably non-woven tissue are essentially aligned along one specific direction.
The present invention also relates to a (on-site or off-site) method for the manufacturing of a system or a free-standing preformed as described above, wherein in a first step at least one free-standing preformed abradable coating element for a turbine or a compressor comprising at least one layer of woven or non-woven tissue or foam material based on fibers made of a material selected from the group of. ceramic, glass, ceramic-metal composite material, and combinations thereof, is made, optionally combined and joined with one or several additional such free-standing preformed abradable coating elements, and wherein in a second optional step the abradable coating system is attached to a turbine or compressor component with a matrix acting as a glue or adhesion promoter, preferably a curable glue cured by irradiation and/or heat.
In the first step of making the free-standing preformed abradable coating element and/or after the second step of attachment thereof on the gas turbine or compressor component the woven or nonwoven tissue or foam can, according to a preferred embodiment of the method, at least partly be embedded in or impregnated with a matrix of a composition of filler particles/fibres and binder, wherein preferably the filler particles/fibres are oxides or oxide precursors and/or wherein preferably the binder is an organic and/or inorganic polymer, and wherein preferably the matrix material is immersed into the tissue material in liquid state and hardened therein. A grading along the radial direction of the turbine and/or compressor in the final coating element can be achieved by differential immersion and/or differential choice of matrix material and/or by using differentially structured layers in the stack of several layers.
A multitude of free-standing, preformed abradable coating element layers with a thickness of up to 4 mm can be produced and subsequently laminated by using for example an adhesion layer to form a final abradable coating system, preferably with a total height in a radial direction (z) in the range of 0.2-4 mm, preferably in the range of 1-2 mm.
7 In the first step, for example in a process using a roll or another source of tissue, is at least partly impregnated by a liquid matrix material of a composition of filler particles/fibres and binder, wherein preferably the filler particles/fibres are oxides or oxide precursors and/or wherein preferably the binder is an organic and/or inorganic polymer, and wherein the structure is optionally pressed and/or cured and/or heated in a compression mould to give a final three-dimensional shape, most preferably with graded properties along the z direction.
In addition to that the present invention relates to a method for the repair (on-site or off-site) of an abradable coating portion of a turbine or a compressor component, wherein in a first optional step the damaged portion is at least partly removed and/or cleaned and/or surface treated, and wherein in a second step at least one free-standing preformed abradable coating element as described above or a complete abradable coating system as described above is attached to the component, preferably by using a curable matrix/glue, wherein preferably only a centre part or a fraction of a centre part is replaced.
A summary of the key aspects of the invention and it main advantages can be given as follows:
= no need for a tip reinforcement of the blade/vane;
= application (and repair) on-site possible;
= no limitation for the thickness of the coating and better tolerance compared to coatings applied by thermal spraying;
= better clearance reduction during the whole operation interval;
= smaller risk of damages of component, in particular blade/vane tip;
= smaller risk of coating spallation and subsequent flying object damage, clogging of the cooling air holes in later turbine stage;
= low cost compared with abradable coatings applied by thermal spraying;
= quick fix for plants experiencing performance loss before end of service interval;
= easier run-in procedure or no run-in procedure;
= functional system even after several thousands of operation hours (for example even in case of rotor sagging).
Further embodiments of the invention are laid down in the dependent claims and in the detailed description.
In addition to that the present invention relates to a method for the repair (on-site or off-site) of an abradable coating portion of a turbine or a compressor component, wherein in a first optional step the damaged portion is at least partly removed and/or cleaned and/or surface treated, and wherein in a second step at least one free-standing preformed abradable coating element as described above or a complete abradable coating system as described above is attached to the component, preferably by using a curable matrix/glue, wherein preferably only a centre part or a fraction of a centre part is replaced.
A summary of the key aspects of the invention and it main advantages can be given as follows:
= no need for a tip reinforcement of the blade/vane;
= application (and repair) on-site possible;
= no limitation for the thickness of the coating and better tolerance compared to coatings applied by thermal spraying;
= better clearance reduction during the whole operation interval;
= smaller risk of damages of component, in particular blade/vane tip;
= smaller risk of coating spallation and subsequent flying object damage, clogging of the cooling air holes in later turbine stage;
= low cost compared with abradable coatings applied by thermal spraying;
= quick fix for plants experiencing performance loss before end of service interval;
= easier run-in procedure or no run-in procedure;
= functional system even after several thousands of operation hours (for example even in case of rotor sagging).
Further embodiments of the invention are laid down in the dependent claims and in the detailed description.
8 BRIEF DESCRIPTION OF THE DRAWINGS
Preferred embodiments of the invention are described in the following with reference to the drawings, which are for the purpose of illustrating the present preferred embodiments of the invention and not for the purpose of limiting the same. In the drawings, Fig. 1 shows in a) a top view onto an abradable coating system applied on a component and in b) a radial cut through an abradable coating system according to the invention applied on a component;
Fig. 2 shows a radial cut through a further embodiment of an abradable coating system applied on a component;
Fig. 3 shows a radial cut through a third embodiment of an abradable coating system applied on a component;
Fig. 4 shows a radial cut through a fourth embodiment of an abradable coating system applied on a component;
Fig. 5 shows a radial cut through a fifth embodiment of an abradable coating system applied on a component;
Fig. 6 shows a schematic representation of the orientation of the fibres in the system;
Fig. 7 shows a schematic representation of the production process of a preformed abradable coating element;
Fig. 8 shows a schematic representation of a second embodiment of a production process of a preformed abradable coating element;
Fig. 9 shows a schematic representation of a production process according to a third embodiment of a preformed abradable coating element; and Fig. 10 shows a schematic representation of a production process according to a fourth embodiment of an abradable coating element.
DESCRIPTION OF PREFERRED EMBODIMENTS
Fig. 1 shows in a) top view and in b) a cut perpendicular to the plane of the system and to the direction of the stripes 2/3, so a radial cut (radial with respect to the turbine/compressor axis) through a coating system according to the invention which is mounted on a stator
Preferred embodiments of the invention are described in the following with reference to the drawings, which are for the purpose of illustrating the present preferred embodiments of the invention and not for the purpose of limiting the same. In the drawings, Fig. 1 shows in a) a top view onto an abradable coating system applied on a component and in b) a radial cut through an abradable coating system according to the invention applied on a component;
Fig. 2 shows a radial cut through a further embodiment of an abradable coating system applied on a component;
Fig. 3 shows a radial cut through a third embodiment of an abradable coating system applied on a component;
Fig. 4 shows a radial cut through a fourth embodiment of an abradable coating system applied on a component;
Fig. 5 shows a radial cut through a fifth embodiment of an abradable coating system applied on a component;
Fig. 6 shows a schematic representation of the orientation of the fibres in the system;
Fig. 7 shows a schematic representation of the production process of a preformed abradable coating element;
Fig. 8 shows a schematic representation of a second embodiment of a production process of a preformed abradable coating element;
Fig. 9 shows a schematic representation of a production process according to a third embodiment of a preformed abradable coating element; and Fig. 10 shows a schematic representation of a production process according to a fourth embodiment of an abradable coating element.
DESCRIPTION OF PREFERRED EMBODIMENTS
Fig. 1 shows in a) top view and in b) a cut perpendicular to the plane of the system and to the direction of the stripes 2/3, so a radial cut (radial with respect to the turbine/compressor axis) through a coating system according to the invention which is mounted on a stator
9 heat shield which here is the component 9.
On component 9 there is provided an abradable coating system with a central circumferential stripe (circumferential with respect to a turbine/compressor axis) which is designated as center part 2 bordered on both sides by also circumferential stripes which are designated as side parts 3. The abradability of these parts 2/3 is differential in that the side parts 3 are less abradable so are more resistant to abrasion than the center part 2. This is achieved in that the side parts 3 are formed by tissues with matrix 1, while the center part 2 is formed by a three layer structure comprising a bottom layer which is based on a tissue with matrix 4 designated with reference no. 8, followed by a tissue with matrix 3 designated with reference no. 7 and a surface coating layer based on a tissue with matrix no. 2 designated with reference no. 6. These tissues with different matrices are differing in their abrasion properties.
The layer 5 with low abrasion property defining the side parts 3 has a tissue and/or a matrix providing low abradability.
Within the center part 2, the layers are graded in that the top layer, i.e.
the tissue 6 with matrix 2 has the highest abradability. This is not only provided by a corresponding selection of tissue material and/or tissue density and matrix, but also supplemented by a surface texturing 4, which in this case is a honeycomb surfacial structure of indentations designated with reference no. 4.
This surfacial layer 6 of center part 2 is followed by layer 7, which has a higher resistance to abrasion than layer 6 but still lower abrasion resistance than layer 5.
This layer 7 is followed in the direction of the component 9 by yet another layer 8 with a higher abrasion resistance than layer 7.
It is to be mentioned that the tissue and the matrix give the characteristic (i.e. erosion resistance, durability, abradability, porosity) of the corresponding layer and of the final complete system. The final characteristic can further be altered by the above-mentioned surface texturing. As concerns the tissue the characteristics can be adapted by a corresponding choice of the tissue material and/or by the choice of the corresponding tissue density and/or fibre thickness. As concerns the matrix the properties can be adapted by a corresponding choice of the filler particles/fibres and/or of the bonding agents and optional additional constituents making up the matrix as well as by the degree of impregnation of matrix material.
In an overall summary table 1 lists important elements of the invention differentiating characteristics with respect to the state of the art.
Type of a State-of-the-art Present invention structure/texture Type and Technical Type and Technical for abradable direction of the approach direction of approach coating system structure/texture the structuring In the centimeter Hardness along x Islands of Hardness Along x:
range and y the same materials, along x: different blocks vertically - on the side, a (i.e. different cracked durable and tissues materials erosion impregnated resistant with different - in the center, matrixes) or an easily monoblock (one abradable tissue system impregrated with masking process) Texturing along grid or Optionally, Grid or x-y honeycomb texturing along honeycomb x-y structures achieved by (hot) pressing the tissue. The surface structuring is formed on the main coating body.
In the millimeter - - Along z By blocks (i.e.
range assembly of tissues impregnated with different matrixes) or monoblock (i.e.
graded impregnation of one tissue) In the micrometer Homogeneous in - Oriented along Tissue with range all directions y or x oriented fibers oriented Table 1: Overview over the comparison of the state of the art and the proposed system.
The structure provided in the centimetre range along the x axis is beneficial in order to stabilize the whole coating. In addition in the x-y plane, it creates a labyrinth for the airflow, which reduces the air losses and may improve performance during the start up procedure.
The structure provided in the millimetre and to another degree in a micrometer range is beneficial in order to guarantee better integrity of the system and less risks of blading tip damages.
The most important elements of the proposed approach are summarised in table 2 as given below:
Characteristic Detailed characteristic Shape/ design . Abradable coating system characterised in that:
of the abradable - it is pre-formed:
coating system - it is pre-sintered characterized in that it can be:
- the tissue only - the matrix and the tissue - or it is a green body characterized in that it can be:
- the tissue only - the matrix and the tissue - the tissue and additional organic polymer (in order to reinforce the tissue for an easier application) - it is monoblock or with several blocks - it is designed with texturing in the cm range, e.g. the sides are harder than the middle zone - its surface is optionally textured in the cm range so that it is achieved e.g. by (isostatic hot) pressing or by using polymers with a grid structure or any texturing with preferably a honeycomb structure - its core has a texture in the millimeter and micrometer range textured This type of structuring is characterised in that:
- fibers are oriented in the direction y preferably or x depending of the operating conditions - the matrix can be locally reinforced by abrasive particles/fibres - the matrix is infiltrated in a graded manner along z - its erosion resistance and abradability are graded and is characterised in that:
- the materials are abradable in the plan x-y in the middle zone, where the blading is running in and it is erosion resistant in the plane x-y on the side in order to stabilize the inner coating - in the middle zone, the coating abradability is graded along the direction z, in order to give the best adhesion and the best stability of the layer, integrity of the system and abradability - it can enable cooling of the parts - It is thermally insulating, light weight - its lifetime: min 1 C- cycle Composition = A tissue and a matrix:
of the abradable - The tissue is characterised in that:
coating system - it is made of ceramic or glass or ceramic-metal composite or combinations thereof - it is woven (e.g. textile or cloth) or non woven (e.g. felt) An alternative to the tissue can be to use a foam.
- Matrix is characterised in that it contains a complex composition of filler particles/fibres and binders.
- The filler particles/fibres can be oxide or oxide precursors or non oxide. They can be selected among other criteria on the criteria of their hardness/abrasive potential.
- The binder can be an organic or inorganic polymer. It is applied as a liquid, which is hardened The several different tissues can optionally be combined within one block or be used for different assemblies.
One or several different matrixes can be used within one assembly.
Preparation - see embodiments according to Figs 7-10 and the corresponding of the abradable description or combination thereof, optionally intermediate drying coating system and/or curing is possible Application - On-site mounted or dismounted of the abradable coating system - On metallic substrate (e.g. stator heat shield), which can have a curvature and which have optionally a surface treatment (e.g. rough surface obtained by blasting, rough surface of metallic coating) - the abradable coating is e.g. glued to the metallic substrate and the glue is cured by for example light radiations (for e.g. UV, IR...) or ) heat (for e.g. resistor or heat of the engine...
Thickness Up to 4 mm of the abradable It can be adjusted to the need by a using for example several coating system tissues/tissue layers Repair process Examples:
- only replacement of the central part or full replacement - only replacement of the surfacial coating and not up to the base metal e.g. on mounted or dismounted part Control of the thermo ra by coating quality Table 2: Overview over essential elements of the proposed system.
Fig. 2 with cooling channels shows a second embodiment of an abradable coating system according to the invention. Again along the direction 12 of hot gas flow there are two side parts 3 and a central centre part 2. Again the centre part 2 is made of a tissue/matrix material combination with significantly higher abradability than the material of the surrounding part 3. Both parts, so centre part 2 as well as side parts 3 can be made based on a tissue material with a matrix.
In this case in order to allow an efficient cooling, the abradable sealing system is provided with a groove or channel like structure 10 which, as the system is mounted on substrate 9, allows the flow through of cooling medium such as cooling air 11. In this case there is provided one single cooling channel, it is however also possible to have a row of parallel cooling channels, these may be arranged in a circumferential or in a axial direction or in a combination thereof, it is also possible to have directions in between.
Figure 3 shows a third embodiment with an erosion resistant coating on the side 3 and a more easily abradable coating in the middle part 2 in plane x-y. The coating can be realized in one block (monoblock) by impregnation with different matrix materials according to embodiment according to Fig 8 or by using differing degrees of impregnation.
It can be realized also with 3 separated different blocks or patches according to embodiment according to Fig. 10. In this case, the central part 2 is given as a block of the same height in z direction as the side parts 3.
Yet another third embodiment is illustrated schematically in figure 4. This embodiment is provided with a different porosity and/or erosion resistance along z and in plane x-y. The coating can be realized in one block (monoblock) by impregnation of different matrix materials according to embodiment according to Fig 8. It can also be realized in 4 different blocks according to embodiment according to Fig. 10. In this case there are provided two layers in the central part 2, the abradability properties of which are graded along z (high abradability on the surface), so in contrast to the embodiment according to figure 1, where there are three layers in this central region, and to the embodiment according to figure 3, where there is only one layer in the region 2, here there are two layers 7, 8 with different abrasion properties.
Figure 5 shows yet another embodiment of a coating system with different properties along z and in plane x-y. The coating can be realized in one block by impregnation with different matrix material according to embodiment according to Fig. 8. It can also be realized in 5 different blocks according to embodiment according to Fig. 10. In this case below the structure defining the centre part 2 and the two side parts 3 there is an additional bottom layer 13. This bottom layer 13 can be part of the actual abradable coating system and contribute to the abradability properties thereof, it can however also be an essentially supporting function fulfilling layer, or it can be the adhesion providing layer (glue layer) by means of which the abradable coating system is attached to component 9.
Figure 6 schematically shows the preferred orientation of the fibres making up the tissue, which is the basis at least for the centre part 2 of the abradable coating system. According to figure 6 oriented fibres of the tissue and rotating direction are shown (N.B. the fibre orientation can also be in the other direction depending on the operating conditions). In other words the direction of the fibres is preferably essentially in alignment with the direction of the blading 14. Fibres 15 in this particular orientation have the lowest resistance to the blading coming in to contact with the corresponding abradable coating system.
In the following also a method to preform the abradable coating shall be illustrated and discussed.
Figure 7 shows in a schematic representation a possible moulding or (hot) pressing manufacturing to give the shape and controlled hardness in specific regions.
From a roll 16 of tissue material the tissue material is introduced into the manufacturing process. In this case cut to the appropriate length and then it is impregnated and then preformed in a compression mould 17. In this compression mould 17 pressure and/or temperature or with irradiation (UV, VIS) are used to essentially give the appropriate shape to the pre-form.
The coating element 18 has a centre part 2 and two side parts 3 and on the face directed towards the substrate 9 there is provided a cooling channel 10 similar to the embodiment as displayed in figure 2. The differentiation in abrasion properties in the regions 2/3 is given by either a differential filling of the tissue with matrix material, as concerns the type of matrix material or as concerns the amount of matrix material with which the tissue material is impregnated. The differentiation can also be achieved by surface texturing (e.g. by mould contours as hot pressing) or a combination of these possibilities.
It is also possible to first form in the compression mould 17 and to then impregnate with the matrix material.
Figure 8 shows a different possible production process. In this case the tissue material is introduced into the manufacturing process from roll 16 and in a first step is cut to length to piece 19. Subsequently in the following step a mask 21 is applied to one surface and from 5 the side where the mask is located a spray device 20 sprays matrix material onto the unmasked portions of the tissue material. Correspondingly only the central part is impregnated with matrix material in this step.
In the next step (optionally after drying and/or hardening of the central impregnated part) a corresponding complementary mask 21 is put on top of the partially impregnated matrix
On component 9 there is provided an abradable coating system with a central circumferential stripe (circumferential with respect to a turbine/compressor axis) which is designated as center part 2 bordered on both sides by also circumferential stripes which are designated as side parts 3. The abradability of these parts 2/3 is differential in that the side parts 3 are less abradable so are more resistant to abrasion than the center part 2. This is achieved in that the side parts 3 are formed by tissues with matrix 1, while the center part 2 is formed by a three layer structure comprising a bottom layer which is based on a tissue with matrix 4 designated with reference no. 8, followed by a tissue with matrix 3 designated with reference no. 7 and a surface coating layer based on a tissue with matrix no. 2 designated with reference no. 6. These tissues with different matrices are differing in their abrasion properties.
The layer 5 with low abrasion property defining the side parts 3 has a tissue and/or a matrix providing low abradability.
Within the center part 2, the layers are graded in that the top layer, i.e.
the tissue 6 with matrix 2 has the highest abradability. This is not only provided by a corresponding selection of tissue material and/or tissue density and matrix, but also supplemented by a surface texturing 4, which in this case is a honeycomb surfacial structure of indentations designated with reference no. 4.
This surfacial layer 6 of center part 2 is followed by layer 7, which has a higher resistance to abrasion than layer 6 but still lower abrasion resistance than layer 5.
This layer 7 is followed in the direction of the component 9 by yet another layer 8 with a higher abrasion resistance than layer 7.
It is to be mentioned that the tissue and the matrix give the characteristic (i.e. erosion resistance, durability, abradability, porosity) of the corresponding layer and of the final complete system. The final characteristic can further be altered by the above-mentioned surface texturing. As concerns the tissue the characteristics can be adapted by a corresponding choice of the tissue material and/or by the choice of the corresponding tissue density and/or fibre thickness. As concerns the matrix the properties can be adapted by a corresponding choice of the filler particles/fibres and/or of the bonding agents and optional additional constituents making up the matrix as well as by the degree of impregnation of matrix material.
In an overall summary table 1 lists important elements of the invention differentiating characteristics with respect to the state of the art.
Type of a State-of-the-art Present invention structure/texture Type and Technical Type and Technical for abradable direction of the approach direction of approach coating system structure/texture the structuring In the centimeter Hardness along x Islands of Hardness Along x:
range and y the same materials, along x: different blocks vertically - on the side, a (i.e. different cracked durable and tissues materials erosion impregnated resistant with different - in the center, matrixes) or an easily monoblock (one abradable tissue system impregrated with masking process) Texturing along grid or Optionally, Grid or x-y honeycomb texturing along honeycomb x-y structures achieved by (hot) pressing the tissue. The surface structuring is formed on the main coating body.
In the millimeter - - Along z By blocks (i.e.
range assembly of tissues impregnated with different matrixes) or monoblock (i.e.
graded impregnation of one tissue) In the micrometer Homogeneous in - Oriented along Tissue with range all directions y or x oriented fibers oriented Table 1: Overview over the comparison of the state of the art and the proposed system.
The structure provided in the centimetre range along the x axis is beneficial in order to stabilize the whole coating. In addition in the x-y plane, it creates a labyrinth for the airflow, which reduces the air losses and may improve performance during the start up procedure.
The structure provided in the millimetre and to another degree in a micrometer range is beneficial in order to guarantee better integrity of the system and less risks of blading tip damages.
The most important elements of the proposed approach are summarised in table 2 as given below:
Characteristic Detailed characteristic Shape/ design . Abradable coating system characterised in that:
of the abradable - it is pre-formed:
coating system - it is pre-sintered characterized in that it can be:
- the tissue only - the matrix and the tissue - or it is a green body characterized in that it can be:
- the tissue only - the matrix and the tissue - the tissue and additional organic polymer (in order to reinforce the tissue for an easier application) - it is monoblock or with several blocks - it is designed with texturing in the cm range, e.g. the sides are harder than the middle zone - its surface is optionally textured in the cm range so that it is achieved e.g. by (isostatic hot) pressing or by using polymers with a grid structure or any texturing with preferably a honeycomb structure - its core has a texture in the millimeter and micrometer range textured This type of structuring is characterised in that:
- fibers are oriented in the direction y preferably or x depending of the operating conditions - the matrix can be locally reinforced by abrasive particles/fibres - the matrix is infiltrated in a graded manner along z - its erosion resistance and abradability are graded and is characterised in that:
- the materials are abradable in the plan x-y in the middle zone, where the blading is running in and it is erosion resistant in the plane x-y on the side in order to stabilize the inner coating - in the middle zone, the coating abradability is graded along the direction z, in order to give the best adhesion and the best stability of the layer, integrity of the system and abradability - it can enable cooling of the parts - It is thermally insulating, light weight - its lifetime: min 1 C- cycle Composition = A tissue and a matrix:
of the abradable - The tissue is characterised in that:
coating system - it is made of ceramic or glass or ceramic-metal composite or combinations thereof - it is woven (e.g. textile or cloth) or non woven (e.g. felt) An alternative to the tissue can be to use a foam.
- Matrix is characterised in that it contains a complex composition of filler particles/fibres and binders.
- The filler particles/fibres can be oxide or oxide precursors or non oxide. They can be selected among other criteria on the criteria of their hardness/abrasive potential.
- The binder can be an organic or inorganic polymer. It is applied as a liquid, which is hardened The several different tissues can optionally be combined within one block or be used for different assemblies.
One or several different matrixes can be used within one assembly.
Preparation - see embodiments according to Figs 7-10 and the corresponding of the abradable description or combination thereof, optionally intermediate drying coating system and/or curing is possible Application - On-site mounted or dismounted of the abradable coating system - On metallic substrate (e.g. stator heat shield), which can have a curvature and which have optionally a surface treatment (e.g. rough surface obtained by blasting, rough surface of metallic coating) - the abradable coating is e.g. glued to the metallic substrate and the glue is cured by for example light radiations (for e.g. UV, IR...) or ) heat (for e.g. resistor or heat of the engine...
Thickness Up to 4 mm of the abradable It can be adjusted to the need by a using for example several coating system tissues/tissue layers Repair process Examples:
- only replacement of the central part or full replacement - only replacement of the surfacial coating and not up to the base metal e.g. on mounted or dismounted part Control of the thermo ra by coating quality Table 2: Overview over essential elements of the proposed system.
Fig. 2 with cooling channels shows a second embodiment of an abradable coating system according to the invention. Again along the direction 12 of hot gas flow there are two side parts 3 and a central centre part 2. Again the centre part 2 is made of a tissue/matrix material combination with significantly higher abradability than the material of the surrounding part 3. Both parts, so centre part 2 as well as side parts 3 can be made based on a tissue material with a matrix.
In this case in order to allow an efficient cooling, the abradable sealing system is provided with a groove or channel like structure 10 which, as the system is mounted on substrate 9, allows the flow through of cooling medium such as cooling air 11. In this case there is provided one single cooling channel, it is however also possible to have a row of parallel cooling channels, these may be arranged in a circumferential or in a axial direction or in a combination thereof, it is also possible to have directions in between.
Figure 3 shows a third embodiment with an erosion resistant coating on the side 3 and a more easily abradable coating in the middle part 2 in plane x-y. The coating can be realized in one block (monoblock) by impregnation with different matrix materials according to embodiment according to Fig 8 or by using differing degrees of impregnation.
It can be realized also with 3 separated different blocks or patches according to embodiment according to Fig. 10. In this case, the central part 2 is given as a block of the same height in z direction as the side parts 3.
Yet another third embodiment is illustrated schematically in figure 4. This embodiment is provided with a different porosity and/or erosion resistance along z and in plane x-y. The coating can be realized in one block (monoblock) by impregnation of different matrix materials according to embodiment according to Fig 8. It can also be realized in 4 different blocks according to embodiment according to Fig. 10. In this case there are provided two layers in the central part 2, the abradability properties of which are graded along z (high abradability on the surface), so in contrast to the embodiment according to figure 1, where there are three layers in this central region, and to the embodiment according to figure 3, where there is only one layer in the region 2, here there are two layers 7, 8 with different abrasion properties.
Figure 5 shows yet another embodiment of a coating system with different properties along z and in plane x-y. The coating can be realized in one block by impregnation with different matrix material according to embodiment according to Fig. 8. It can also be realized in 5 different blocks according to embodiment according to Fig. 10. In this case below the structure defining the centre part 2 and the two side parts 3 there is an additional bottom layer 13. This bottom layer 13 can be part of the actual abradable coating system and contribute to the abradability properties thereof, it can however also be an essentially supporting function fulfilling layer, or it can be the adhesion providing layer (glue layer) by means of which the abradable coating system is attached to component 9.
Figure 6 schematically shows the preferred orientation of the fibres making up the tissue, which is the basis at least for the centre part 2 of the abradable coating system. According to figure 6 oriented fibres of the tissue and rotating direction are shown (N.B. the fibre orientation can also be in the other direction depending on the operating conditions). In other words the direction of the fibres is preferably essentially in alignment with the direction of the blading 14. Fibres 15 in this particular orientation have the lowest resistance to the blading coming in to contact with the corresponding abradable coating system.
In the following also a method to preform the abradable coating shall be illustrated and discussed.
Figure 7 shows in a schematic representation a possible moulding or (hot) pressing manufacturing to give the shape and controlled hardness in specific regions.
From a roll 16 of tissue material the tissue material is introduced into the manufacturing process. In this case cut to the appropriate length and then it is impregnated and then preformed in a compression mould 17. In this compression mould 17 pressure and/or temperature or with irradiation (UV, VIS) are used to essentially give the appropriate shape to the pre-form.
The coating element 18 has a centre part 2 and two side parts 3 and on the face directed towards the substrate 9 there is provided a cooling channel 10 similar to the embodiment as displayed in figure 2. The differentiation in abrasion properties in the regions 2/3 is given by either a differential filling of the tissue with matrix material, as concerns the type of matrix material or as concerns the amount of matrix material with which the tissue material is impregnated. The differentiation can also be achieved by surface texturing (e.g. by mould contours as hot pressing) or a combination of these possibilities.
It is also possible to first form in the compression mould 17 and to then impregnate with the matrix material.
Figure 8 shows a different possible production process. In this case the tissue material is introduced into the manufacturing process from roll 16 and in a first step is cut to length to piece 19. Subsequently in the following step a mask 21 is applied to one surface and from 5 the side where the mask is located a spray device 20 sprays matrix material onto the unmasked portions of the tissue material. Correspondingly only the central part is impregnated with matrix material in this step.
In the next step (optionally after drying and/or hardening of the central impregnated part) a corresponding complementary mask 21 is put on top of the partially impregnated matrix
10 material, so a mask covering the area in the centre 2 which has already been impregnated but leaving free the side portions 3. Now again using spray devices 20 these side portions are impregnated. The differentiation between the centre portion 2 and the side portions 3 is either achieved by spraying different types of matrix material in the two subsequent steps or by spraying a different amount of matrix material in the subsequent steps.
15 After this step, optionally followed by a specific hardening and /or shaping step in a compression mould, the final preformed abradable coating element 18 is ready.
It should be noted that between the two steps with spraying the matrix material also a hardening and/or shaping step can be inserted.
Figure 9 shows yet another possible manufacturing process for a multilayer structure. An element as produced as a result of process according to figure 8 is on at least one side preferably sprayed with a spray device 26 with an adhesion layer and a second element as produced in a process according to figure 8 is put on top sandwiching the adhesion layer 23 leading to a multilayer preformed abradable coating element 18. This processing can be repeated several times building up a multilayer stack, wherein it is for example also possible to stack elements 22 with consecutively increasing abradablility of the centre part leading to the above-mentioned grading of the abrasion properties along z in particular in the centre portion 2.
Figure 10 shows a preparation by block. In individual processing steps cut to length pieces 19 are completely sprayed by devices 20 but differently leading on the one hand to highly abradable centre part patches 27 and to less easily abradable side part layer 28. These layers 27/28 are then mounted on a component 9 as illustrated on the right hand side, for example by first attaching/gluing the side part elements 28 by leaving an inter-space and in a subsequent step adding the centre part element 27 in the middle. Of course this sequence can also be reversed depending on the circumstances.
LIST OF REFERENCE SIGNS
1 blade rotation direction abradable coating element 2 centre part 23 adhesion layer 3 side part 24 second layer of preformed 4 surface texturing abradable coating element tissue with matrix 1 6 tissue with matrix 2 26 glue/adhesion layer spray 7 tissue with matrix 3 device 8 tissue with matrix 4 27 center part layer 9 substrate 28 side part layer cooling channel
15 After this step, optionally followed by a specific hardening and /or shaping step in a compression mould, the final preformed abradable coating element 18 is ready.
It should be noted that between the two steps with spraying the matrix material also a hardening and/or shaping step can be inserted.
Figure 9 shows yet another possible manufacturing process for a multilayer structure. An element as produced as a result of process according to figure 8 is on at least one side preferably sprayed with a spray device 26 with an adhesion layer and a second element as produced in a process according to figure 8 is put on top sandwiching the adhesion layer 23 leading to a multilayer preformed abradable coating element 18. This processing can be repeated several times building up a multilayer stack, wherein it is for example also possible to stack elements 22 with consecutively increasing abradablility of the centre part leading to the above-mentioned grading of the abrasion properties along z in particular in the centre portion 2.
Figure 10 shows a preparation by block. In individual processing steps cut to length pieces 19 are completely sprayed by devices 20 but differently leading on the one hand to highly abradable centre part patches 27 and to less easily abradable side part layer 28. These layers 27/28 are then mounted on a component 9 as illustrated on the right hand side, for example by first attaching/gluing the side part elements 28 by leaving an inter-space and in a subsequent step adding the centre part element 27 in the middle. Of course this sequence can also be reversed depending on the circumstances.
LIST OF REFERENCE SIGNS
1 blade rotation direction abradable coating element 2 centre part 23 adhesion layer 3 side part 24 second layer of preformed 4 surface texturing abradable coating element tissue with matrix 1 6 tissue with matrix 2 26 glue/adhesion layer spray 7 tissue with matrix 3 device 8 tissue with matrix 4 27 center part layer 9 substrate 28 side part layer cooling channel
11 cooling air
12 direction of hot gas flow h height of abradable coating
13 additional bottom layer system in radial direction
14 blading x direction parallel to hot gas fibres of tissue flow, axial direction 16 roll of tissue material y direction perpendicular to hot 17 mould gas flow and parallel to 18 preformed abradable coating blading direction element z radial direction with respect 19 cut to length piece to turbine/compressor axis matrix material spray device 21 mask 22 one layer of preformed
Claims (16)
1. Abradable coating system (2-8) for clearance reduction in a turbine or a compressor comprising at least one block wherein the block comprises a woven or non-woven tissue (15) or foam made of a material selected from the group of ceramic, glass, glass-ceramic, ceramic-metal composite and combinations thereof, which is at least partly filled with filler particles and/or filler fibres and/or with a binder of an inorganic polymer.
2. Abradable coating system according to claim 1, wherein at least in a centre part (2) of the system the abradability is graded along a radial direction (z) with respect to a turbine/compressor axis such that the surfacial region of the side facing a blading (14) is more abradable than the opposite side facing a component (9) on which the system is applied, wherein preferably the grading is achieved by different layers or by a grading within a layer, and wherein further preferably differentiation between the layers, in particular within a central part (2) is provided by using for each layer the same tissue but providing a different impregnation (4) in each layer or a graded impregnation in one layer, wherein further preferably the impregnation differs by type and/or density of filler particles (4) and/or filler fibres and/or by different type and/or density of binder material.
3. Abradable coating system according to claim 1 or 2, wherein it comprises a stripe- like circumferentially oriented centre part (2) bordered, preferably at both sides in axial direction, by a stripe like circumferentially oriented side part (3), wherein the centre part (2) is highly abradable such that it is essentially abraded by a blading (14), preferably without blading tip reinforcement, and wherein the side part(s) (3) are less or essentially not abradable and erosion resistant, wherein preferably the centre part (2) has a width in the axial direction of at least one third of the width of the tip portion of the blading (14).
4. Abradable coating system according to any of the preceding claims, wherein the filler particles or filler fibres are particles/fibres based on a material selected from the group of ceramic, glass, glass-ceramic, ceramic-metal composite and combinations thereof, preferably based on yttrium stabilized zirconia, aluminum oxide, silicon dioxide, aluminum hydroxide, silicon carbide, cerium oxide, aluminum toughened zirconia, and/or wherein the inorganic binder is selected from the group of alkali silicate, alumino silicate, aluminum phosphate
5. Abradable coating system according to any of the preceding claims with a height (h) along the radial direction (z) with respect to the turbine or compressor axis in the range of 0.2-4 mm, preferably in the range of 1-2 mm.
6. Abradable coating system according to any of the preceding claims, wherein the surface of the centre part (2) is provided with a surface texturing (4), preferably with dimensions along the radial direction (z) with respect to the turbine/compressor axis in the range of 0.1-4 mm, wherein further preferably the surface texturing (4) is a pattern, preferably a honeycomb pattern.
7. Abradable coating system according to any of the preceding claims, wherein it is provided with cooling elements (10), wherein preferably these cooling elements are provided as channels and/or grooves in the at least one block.
8. Abradable coating system according to any of the preceding claims, wherein it is a monoblock or an assembly of several blocks, wherein preferably the monoblock or at least one block of such an assembly is a multilayer assembly of several individual abradable coating layers, and wherein preferentially individual abradable coating layers of the multilayer assembly have a thickness of 0.1 mm to 4 mm.
9. Abradable coating system according to any of the preceding claims, wherein it comprises a stripe-like circumferentially oriented centre part (2) bordered, preferably at both sides in axial direction, by a stripe like circumferentially oriented side part (3), wherein the centre part (2) is highly abradable such that it is essentially abraded by the blading (14), preferably without blading tip reinforcement, and wherein the side part(s) (3) are less or essentially not abradable, and erosion resistant, wherein the abradability differentiation between centre part (2) and side part(s) (3) is provided by using for both parts the same tissue but providing a different impregnation in the centre part (2) than in the side part(s) (3), wherein preferably the impregnation differs by type and/or density of filler particles (4) /fibres and/or by different type and/or density of binder material.
10. Abradable coating system according to any of the preceding claims, wherein the fibres (15) of the woven or non-woven tissue are essentially aligned along the rotation direction (1), wherein preferably at least in the surface region the system comprises a stripe-like circumferentially oriented centre part (2) based on a layer of woven or non-woven tissue bordered, preferably at both sides in axial direction, by a stripe-like circumferentially oriented side part (3), wherein in the centre part (2) the fibres (15) of the woven or non-woven tissue are essentially aligned along the rotation direction (1) and wherein the centre part (2) is highly abradable such that it is essentially abraded by a blade or a vane (14), preferably without blading tip reinforcement, and preferably erosion resistant, and wherein the side part(s) (3) are less abradable, and erosion resistant, wherein preferably the centre part (2) has a width in the axial direction at least identical to one third of the width of the tip portion of the corresponding blading (14).
11. Abradable coating system according to any of the preceding claims, wherein it is applied on a turbine or compressor component (9), preferably in a circumferential indentation thereof, and wherein preferably it is attached on the component (9) with a matrix, preferably with a matrix similar or essentially the same as the one used for the impregnation.
12. Method for the preparation of an abradable coating system according to any of preceding claims on a turbine or compressor component (9), wherein either in a first step the woven or non-woven tissue or foam made of a material selected from the group of ceramic, glass, glass-ceramic, ceramic-metal composite and combinations thereof is attached to a turbine or compressor component (9) with a matrix, preferably based on filler particles and/or filler fibres selected from oxide precursor, oxideand combinations thereof and/or a binder selected from the group of organic or inorganic polymer, and in a second step the woven or non-woven tissue or foam is impregnated with filler particles/fibres selected from the group of oxide precursor, oxide and combinations thereof and/or a binder selected from the group of organic and inorganic polymer, wherein in an optional additional step at least another woven or non-woven tissues or foams is combined and joined to the abradable coating system or in a first step the woven or non-woven tissue or foam made of a material selected from the group of ceramic, glass, glass-ceramic, ceramic-metal composite and combinations thereof is impregnated with filler particles/fibres selected from the group of oxide precursor, oxide and combinations thereof and/or a binder selected from the group of organic and inorganic polymer, and is optionally pre-sintered, and in a second step the impregnated matrix material is attached to a turbine or compressor component (9) with a matrix, preferably based on filler particles/fibres selected from oxide precursor, oxide and combinations thereof and/or a binder selected from the group of organic or inorganic polymer, wherein in an optional additional step at least one additional such impregnated woven or non-woven tissue or foam is joined to the abradable coating system and wherein a third step the abradable coating system is heat treated.
13. Method according to claim 12, wherein a grading along the radial direction (z) of the abradable coating system (18) is achieved by differential impregnation and/or differential choice of matrix.
14. Method according to any of the preceding claims 12-13, wherein a multitude of free-standing preformed abradable coating elements with a thickness of 0.1 mm to 4 mm are produced and subsequently assembled by using adhesion layers (23) to form a final abradable coating system, preferably with a total height (h) in a radial direction (z) in the range of 0.2-4 mm, preferably in the range of 1-2 mm and/or wherein the abradable coating system is pressed and/or cured and/or heated in a mould (17) to give a final three-dimensional shape, optionally with graded properties.
15. Free-standing preformed abradable coating element (18) comprising at least one layer of woven or non-woven tissue or foam made of a material selected from the group of ceramic, glass, glass-ceramic, ceramic-metal composite material and combinations thereof, wherein it is filled with filler particles/fibres selected from the group of ceramic, glass, glass-ceramic and combinations thereof and/or a binder of inorganic polymer.
16. Method for the repair of an abradable coating portion of a turbine or a compressor component (9), wherein in a first optional step, optionally after an inspection of the coating using for example thermography, the damaged portion is at least partly removed and/or cleaned and/or surface treated, and wherein in a second step at least one free-standing preformed abradable coating element (18) according to claim 15 or a complete abradable coating system according to any of claims 1-is attached to the component (9), preferably a metal component, further preferably by using a matrix, preferably with a similar composition than the matrix used for the impregnation, wherein preferably only a centre part (2) or a fraction of a centre part (2) is replaced, optionally followed by an inspection of the repaired coating using for example thermography.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US25639309P | 2009-10-30 | 2009-10-30 | |
| US61/256,393 | 2009-10-30 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2717827A1 true CA2717827A1 (en) | 2011-04-30 |
| CA2717827C CA2717827C (en) | 2016-09-27 |
Family
ID=43513953
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2717827A Expired - Fee Related CA2717827C (en) | 2009-10-30 | 2010-10-15 | Abradable coating system |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US8821116B2 (en) |
| EP (1) | EP2317079B1 (en) |
| CA (1) | CA2717827C (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11149354B2 (en) | 2019-02-20 | 2021-10-19 | General Electric Company | Dense abradable coating with brittle and abradable components |
Families Citing this family (35)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9175575B2 (en) * | 2012-01-04 | 2015-11-03 | General Electric Company | Modification of turbine engine seal abradability |
| US9145775B2 (en) | 2012-03-02 | 2015-09-29 | United Technologies Corporation | Tapered thermal coating for airfoil |
| US10215033B2 (en) * | 2012-04-18 | 2019-02-26 | General Electric Company | Stator seal for turbine rub avoidance |
| FR2991374B1 (en) * | 2012-06-04 | 2016-04-08 | Snecma | STATOR WINDOW OF TURBOMACHINE COVERED WITH ABRADABLE COATING |
| US9598973B2 (en) | 2012-11-28 | 2017-03-21 | General Electric Company | Seal systems for use in turbomachines and methods of fabricating the same |
| US20160003083A1 (en) * | 2013-02-19 | 2016-01-07 | United Technologies Corporation | Abradable seal including an abradability characteristic that varies by locality |
| EP3052787B1 (en) | 2013-10-02 | 2021-12-15 | Raytheon Technologies Corporation | Air seal system and method for forming an air seal system |
| DE102013223585A1 (en) * | 2013-11-19 | 2015-06-03 | MTU Aero Engines AG | Inlet lining based on metal fibers |
| US9957819B2 (en) | 2014-03-28 | 2018-05-01 | United Technologies Corporation | Abrasive tip blade manufacture methods |
| DE102014208801A1 (en) * | 2014-05-09 | 2015-11-12 | MTU Aero Engines AG | Seal, method for producing a seal and turbomachine |
| US20150354392A1 (en) * | 2014-06-10 | 2015-12-10 | General Electric Company | Abradable coatings |
| US20150354394A1 (en) * | 2014-06-10 | 2015-12-10 | General Electric Company | Shroud abradable coatings and methods of manufacturing |
| US20150354393A1 (en) * | 2014-06-10 | 2015-12-10 | General Electric Company | Methods of manufacturing a shroud abradable coating |
| GB201419412D0 (en) | 2014-10-31 | 2014-12-17 | Rolls Royce Plc | Rotary device |
| US10834790B2 (en) * | 2014-12-22 | 2020-11-10 | Rolls-Royce High Temperature Composites, Inc. | Method for making ceramic matrix composite articles with progressive melt infiltration |
| US10406640B2 (en) | 2014-12-22 | 2019-09-10 | Rolls-Royce High Temperature Composites, Inc. | Method for repairing ceramic matrix composite (CMC) articles |
| US10273192B2 (en) | 2015-02-17 | 2019-04-30 | Rolls-Royce Corporation | Patterned abradable coating and methods for the manufacture thereof |
| US20160305319A1 (en) * | 2015-04-17 | 2016-10-20 | General Electric Company | Variable coating porosity to influence shroud and rotor durability |
| US10458653B2 (en) * | 2015-06-05 | 2019-10-29 | Rolls-Royce Corporation | Machinable CMC insert |
| US10465534B2 (en) * | 2015-06-05 | 2019-11-05 | Rolls-Royce North American Technologies, Inc. | Machinable CMC insert |
| US10472976B2 (en) * | 2015-06-05 | 2019-11-12 | Rolls-Royce Corporation | Machinable CMC insert |
| US10030305B2 (en) | 2015-11-19 | 2018-07-24 | General Electric Company | Method to protect features during repair cycle |
| FR3044946B1 (en) * | 2015-12-14 | 2018-01-12 | Safran Aircraft Engines | ABRADABLE COATING WITH VARIABLE DENSITY |
| FR3044945B1 (en) * | 2015-12-14 | 2018-01-12 | Centre National De La Recherche Scientifique | ABRADABLE COATING WITH VARIABLE DENSITY |
| US10794221B2 (en) * | 2017-04-25 | 2020-10-06 | United Technologies Corporation | Gas turbine engine with geopolymer seal element |
| US11313243B2 (en) * | 2018-07-12 | 2022-04-26 | Rolls-Royce North American Technologies, Inc. | Non-continuous abradable coatings |
| US11773872B2 (en) * | 2018-10-04 | 2023-10-03 | Honda Motor Co., Ltd. | Ducted fan device |
| FR3087195B1 (en) | 2018-10-11 | 2022-01-28 | Safran Aircraft Engines | METHOD FOR MANUFACTURING A POROUS ABRADABLE COATING IN CERAMIC MATERIAL |
| CN111089077B (en) * | 2018-10-24 | 2024-08-09 | 汉江弘源襄阳碳化硅特种陶瓷有限责任公司 | Wear-resistant silicon carbide ceramic impeller |
| US11274828B2 (en) | 2019-02-08 | 2022-03-15 | Raytheon Technologies Corporation | Article with bond coat layer and layer of networked ceramic nanofibers |
| US11591918B2 (en) | 2019-02-08 | 2023-02-28 | Raytheon Technologies Corporation | Article with ceramic barrier coating and layer of networked ceramic nanofibers |
| DE102019201658A1 (en) * | 2019-02-08 | 2020-08-13 | MTU Aero Engines AG | PROCEDURE FOR RENEWING AN INTAKE LAYERING OF A CASE-ELECTRIC POWER PLANT |
| US10919180B2 (en) | 2019-02-08 | 2021-02-16 | Raytheon Technologies Corporation | Repair process using networked ceramic nanofibers |
| EP3822004A1 (en) * | 2019-11-14 | 2021-05-19 | Rolls-Royce Corporation | Fused filament fabrication of abradable coatings |
| US11215070B2 (en) * | 2019-12-13 | 2022-01-04 | Pratt & Whitney Canada Corp. | Dual density abradable panels |
Family Cites Families (61)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3970319A (en) * | 1972-11-17 | 1976-07-20 | General Motors Corporation | Seal structure |
| US4323756A (en) | 1979-10-29 | 1982-04-06 | United Technologies Corporation | Method for fabricating articles by sequential layer deposition |
| US4595637A (en) * | 1981-11-17 | 1986-06-17 | United Technologies Corporation | Plasma coatings comprised of sprayed fibers |
| US4422648A (en) * | 1982-06-17 | 1983-12-27 | United Technologies Corporation | Ceramic faced outer air seal for gas turbine engines |
| US4738902A (en) * | 1983-01-18 | 1988-04-19 | United Technologies Corporation | Gas turbine engine and composite parts |
| CH664317A5 (en) | 1983-08-09 | 1988-02-29 | Hauni Werke Koerber & Co Kg | METHOD AND DEVICE FOR RELEASING CASTING BLOCKS OF WORKPIECES. |
| JPS60238489A (en) | 1984-05-12 | 1985-11-27 | Daiki Gomme Kogyo Kk | Formatin of metallic coating layer on surface |
| US4968383A (en) | 1985-06-18 | 1990-11-06 | The Dow Chemical Company | Method for molding over a preform |
| DE3832351A1 (en) * | 1988-09-23 | 1990-04-05 | Schock & Co Gmbh | COMPONENT, IN PARTICULAR BUILT-IN COIL AND METHOD FOR THE PRODUCTION THEREOF |
| US5876550A (en) | 1988-10-05 | 1999-03-02 | Helisys, Inc. | Laminated object manufacturing apparatus and method |
| US5038014A (en) | 1989-02-08 | 1991-08-06 | General Electric Company | Fabrication of components by layered deposition |
| US5047966A (en) | 1989-05-22 | 1991-09-10 | Airfoil Textron Inc. | Airfoil measurement method |
| US5156697A (en) | 1989-09-05 | 1992-10-20 | Board Of Regents, The University Of Texas System | Selective laser sintering of parts by compound formation of precursor powders |
| US5121329A (en) | 1989-10-30 | 1992-06-09 | Stratasys, Inc. | Apparatus and method for creating three-dimensional objects |
| US5269057A (en) | 1991-12-24 | 1993-12-14 | Freedom Forge Corporation | Method of making replacement airfoil components |
| DE4432685C1 (en) * | 1994-09-14 | 1995-11-23 | Mtu Muenchen Gmbh | Starting cover for turbo=machine casing |
| US5900170A (en) | 1995-05-01 | 1999-05-04 | United Technologies Corporation | Containerless method of producing crack free metallic articles by energy beam deposition with reduced power density |
| DE19642980C1 (en) | 1996-10-18 | 1998-08-13 | Mtu Muenchen Gmbh | Procedure for repairing worn blade tips of compressor and turbine blades |
| US6144008A (en) | 1996-11-22 | 2000-11-07 | Rabinovich; Joshua E. | Rapid manufacturing system for metal, metal matrix composite materials and ceramics |
| DE19649865C1 (en) | 1996-12-02 | 1998-02-12 | Fraunhofer Ges Forschung | Shaped body especially prototype or replacement part production |
| US5951892A (en) * | 1996-12-10 | 1999-09-14 | Chromalloy Gas Turbine Corporation | Method of making an abradable seal by laser cutting |
| US6355086B2 (en) | 1997-08-12 | 2002-03-12 | Rolls-Royce Corporation | Method and apparatus for making components by direct laser processing |
| US6057047A (en) * | 1997-11-18 | 2000-05-02 | United Technologies Corporation | Ceramic coatings containing layered porosity |
| US6203861B1 (en) | 1998-01-12 | 2001-03-20 | University Of Central Florida | One-step rapid manufacturing of metal and composite parts |
| US6064031A (en) | 1998-03-20 | 2000-05-16 | Mcdonnell Douglas Corporation | Selective metal matrix composite reinforcement by laser deposition |
| US6733907B2 (en) * | 1998-03-27 | 2004-05-11 | Siemens Westinghouse Power Corporation | Hybrid ceramic material composed of insulating and structural ceramic layers |
| US7563504B2 (en) * | 1998-03-27 | 2009-07-21 | Siemens Energy, Inc. | Utilization of discontinuous fibers for improving properties of high temperature insulation of ceramic matrix composites |
| US6583381B1 (en) | 1999-05-24 | 2003-06-24 | Potomac Photonics, Inc. | Apparatus for fabrication of miniature structures |
| DE19928245B4 (en) | 1999-06-21 | 2006-02-09 | Eos Gmbh Electro Optical Systems | Device for supplying powder for a laser sintering device |
| DE19935274C1 (en) | 1999-07-27 | 2001-01-25 | Fraunhofer Ges Forschung | Apparatus for producing components made of a material combination has a suction and blowing device for removing material from the processing surface, and a feed device for a further material |
| ATE420272T1 (en) | 1999-12-20 | 2009-01-15 | Sulzer Metco Ag | PROFILED SURFACE USED AS A SCRUB COATING IN FLOW MACHINES |
| US6365222B1 (en) * | 2000-10-27 | 2002-04-02 | Siemens Westinghouse Power Corporation | Abradable coating applied with cold spray technique |
| US6435824B1 (en) * | 2000-11-08 | 2002-08-20 | General Electric Co. | Gas turbine stationary shroud made of a ceramic foam material, and its preparation |
| US6508000B2 (en) | 2001-02-08 | 2003-01-21 | Siemens Westinghouse Power Corporation | Transient liquid phase bonding repair for advanced turbine blades and vanes |
| US6537021B2 (en) | 2001-06-06 | 2003-03-25 | Chromalloy Gas Turbine Corporation | Abradeable seal system |
| DE10131362A1 (en) | 2001-06-28 | 2003-01-09 | Alstom Switzerland Ltd | Process for producing a spatially shaped, film-like carrier layer made of brittle hard material |
| WO2003010419A1 (en) | 2001-07-23 | 2003-02-06 | Alstom Technology Ltd | Device for reducing sealing gaps between moving and stationary components inside a non-positive-displacement machine |
| US20030082297A1 (en) * | 2001-10-26 | 2003-05-01 | Siemens Westinghouse Power Corporation | Combustion turbine blade tip restoration by metal build-up using thermal spray techniques |
| US6820334B2 (en) * | 2002-04-19 | 2004-11-23 | General Electric Company | Method for repairing articles of ceramic composites |
| DE10219983B4 (en) | 2002-05-03 | 2004-03-18 | Bego Medical Ag | Process for manufacturing products using free-form laser sintering |
| US6838157B2 (en) | 2002-09-23 | 2005-01-04 | Siemens Westinghouse Power Corporation | Method and apparatus for instrumenting a gas turbine component having a barrier coating |
| US6912446B2 (en) | 2002-10-23 | 2005-06-28 | General Electric Company | Systems and methods for automated sensing and machining for repairing airfoils of blades |
| US6887528B2 (en) * | 2002-12-17 | 2005-05-03 | General Electric Company | High temperature abradable coatings |
| US6916529B2 (en) * | 2003-01-09 | 2005-07-12 | General Electric Company | High temperature, oxidation-resistant abradable coatings containing microballoons and method for applying same |
| DE10319494A1 (en) | 2003-04-30 | 2004-11-18 | Mtu Aero Engines Gmbh | Process for repairing and / or modifying components of a gas turbine |
| DE10334698A1 (en) * | 2003-07-25 | 2005-02-10 | Rolls-Royce Deutschland Ltd & Co Kg | Shroud segment for a turbomachine |
| US20050123785A1 (en) | 2003-12-04 | 2005-06-09 | Purusottam Sahoo | High temperature clearance coating |
| DE102004063489B3 (en) | 2004-12-23 | 2006-08-31 | Greiwe, Reinhard, Dipl.-Ing. | Method for producing a lightweight component from hollow spheres |
| ATE405686T1 (en) | 2005-06-16 | 2008-09-15 | Sulzer Metco Us Inc | ALUMINUM OXIDE DOPED WEARABLE CERAMIC MATERIAL |
| US20070141375A1 (en) | 2005-12-20 | 2007-06-21 | Budinger David E | Braze cladding for direct metal laser sintered materials |
| US20070274854A1 (en) * | 2006-05-23 | 2007-11-29 | General Electric Company | Method of making metallic composite foam components |
| US7686570B2 (en) | 2006-08-01 | 2010-03-30 | Siemens Energy, Inc. | Abradable coating system |
| GB0616116D0 (en) | 2006-08-12 | 2006-09-20 | Rolls Royce Plc | A method of forming a component on a substrate |
| DE102006049218A1 (en) | 2006-10-18 | 2008-04-30 | Mtu Aero Engines Gmbh | Method for producing a gas turbine component |
| US20080182017A1 (en) | 2007-01-31 | 2008-07-31 | General Electric Company | Laser net shape manufacturing and repair using a medial axis toolpath deposition method |
| US8691329B2 (en) | 2007-01-31 | 2014-04-08 | General Electric Company | Laser net shape manufacturing using an adaptive toolpath deposition method |
| GB0705696D0 (en) | 2007-03-24 | 2007-05-02 | Rolls Royce Plc | A method of repairing a damaged abradable coating |
| DK200700647A (en) | 2007-04-30 | 2008-05-10 | Lm Glasfiber As | Measurement of geometric parameters for a wind turbine blade |
| DE102007029052A1 (en) | 2007-06-21 | 2009-01-02 | Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. | Method and device for producing a component based on three-dimensional data of the component |
| US8309197B2 (en) * | 2008-12-17 | 2012-11-13 | Teledyne Scientific & Imaging, Llc | Integral abradable seals |
| DE102009034025A1 (en) * | 2009-07-21 | 2011-01-27 | Mtu Aero Engines Gmbh | Inlet lining for arrangement on a gas turbine component |
-
2010
- 2010-10-04 EP EP10186341.3A patent/EP2317079B1/en active Active
- 2010-10-15 CA CA2717827A patent/CA2717827C/en not_active Expired - Fee Related
- 2010-10-29 US US12/915,978 patent/US8821116B2/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11149354B2 (en) | 2019-02-20 | 2021-10-19 | General Electric Company | Dense abradable coating with brittle and abradable components |
Also Published As
| Publication number | Publication date |
|---|---|
| CA2717827C (en) | 2016-09-27 |
| EP2317079B1 (en) | 2020-05-20 |
| US8821116B2 (en) | 2014-09-02 |
| EP2317079A3 (en) | 2013-09-25 |
| EP2317079A2 (en) | 2011-05-04 |
| US20110103940A1 (en) | 2011-05-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2717827C (en) | Abradable coating system | |
| CN107667007B (en) | Sandwich arrangement with ceramic faceplates and ceramic felt | |
| US9784113B2 (en) | Method of fabricating a turbine or compressor guide vane sector made of composite material for a turbine engine, and a turbine or a compressor incorporating such guide vane sectors | |
| CA2744896C (en) | Composite material turbomachine engine vane and method for manufacturing same | |
| JP4814611B2 (en) | Ceramic composite with integrated compliance / wear layer | |
| US9045992B2 (en) | Turbomachine blades or vanes having complementary even/odd geometry | |
| EP1674599B1 (en) | Orthogonal weaving for fabricating complex shape preforms | |
| US8100640B2 (en) | Blade outer air seal with improved thermomechanical fatigue life | |
| EP3736414B1 (en) | Abrasive tip blade and manufacture method | |
| KR20150126054A (en) | Method and apparatus for fabrication and repair of thermal barriers | |
| US20130122259A1 (en) | Features for mitigating thermal or mechanical stress on an environmental barrier coating | |
| US20050003172A1 (en) | 7FAstage 1 abradable coatings and method for making same | |
| US20140241900A1 (en) | Methods for repairing a turbine airfoil constructed from cmc material | |
| US20090311552A1 (en) | Component with a reinforcing plating | |
| US20220134690A1 (en) | Repair or resumption of manufacture of a composite material part with fibrous three-dimensional woven reinforcement | |
| GB2529854A (en) | Rotary blade tip | |
| KR20150067359A (en) | Rotor-stator assembly for a gas- turbine engine | |
| CN108367359B (en) | Wear resistant coating with variable density | |
| US20180087387A1 (en) | Compositions and methods for coating metal turbine blade tips | |
| CN110872954A (en) | CMC component including directionally controllable CMC insert and method of making | |
| US12023881B2 (en) | Composite component void repair | |
| US20090223632A1 (en) | Abradable material composition, a thermomechanical part or casing including a coating, and a method of fabricating or repairing a coating presenting said composition | |
| CN117183413A (en) | Repairing or restoring production of components made of composite material | |
| WO2018164693A1 (en) | Three-dimensional printing of ceramic fiber composite structures for improved thermal barrier coating adhesion | |
| CN111322125A (en) | Coating for improving surface finish |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request |
Effective date: 20131008 |
|
| MKLA | Lapsed |
Effective date: 20191015 |